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Int. J. Turbomach. Propuls. Power 2017, 2(1), 1; doi:10.3390/ijtpp2010001

Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade

German Aerospace Center DLR, Institute of Propulsion Technology, Department Fan and Compressor, 51170 Köln, Germany
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Academic Editor: Marcello Manna
Received: 15 September 2016 / Revised: 17 February 2017 / Accepted: 23 February 2017 / Published: 16 March 2017
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Abstract

The following paper deals with the development of an optimized non-axisymmetric endwall contour for reducing the total pressure loss and for homogenizing the outflow of a highly-loaded compressor cascade. In contrast to former studies using a NACA-65 K48 cascade airfoil this study starts with the design of a new high-performance airfoil which is based on the aerodynamic boundary conditions of the NACA-65 K48 cascade. This new airfoil is then used as a basis. Optimizations of the airfoil and of the endwall contour are performed using the German Aerospace Center (DLR) in-house tool AutoOpti and the RANS (Reynolds-averaged Navier-Stokes)-solver TRACE (Turbomachinery Research Aerodynamic Computational Environment). Three operating points at an inflow Mach number of 0.67 with different inflow angles are used to secure a wide operating range. The optimized endwall contour changes the secondary flow in such a way that the corner stall is reduced which, in turn, significantly reduces the total pressure loss. The endwall contour in the outflow region leads to a considerable homogenization of the outflow in the near wall region. Using non-axisymmetric endwall shaping demonstrates a valuable measure to further improve highly-efficient compressor blading on the vane level. View Full-Text
Keywords: compressor; CFD; optimization; endwall contouring; cascade; outflow angle; overturning; secondary flow; corner stall compressor; CFD; optimization; endwall contouring; cascade; outflow angle; overturning; secondary flow; corner stall
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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MDPI and ACS Style

Reutter, O.; Rozanski, M.; Hergt, A.; Nicke, E. Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade. Int. J. Turbomach. Propuls. Power 2017, 2, 1.

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Int. J. Turbomach. Propuls. Power EISSN 2504-186X Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
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